Record and playback system for aircraft

ABSTRACT

Multiple data and images are multiplexed and sequenced in order to minimize the recording and monitoring hardware required to process the images, providing a detailed record of an event, greatly enhancing event reconstruction efforts. The multi-media safety and surveillance system for aircraft incorporates a plurality of strategically spaced sensors including video imaging generators for monitoring critical components and critical areas of both the interior and the exterior of the aircraft. The captured data and images are recorded and may be transmitted to ground control stations for real time or near real time surveillance. The system includes a plurality of strategically located video image sensors such as, by way of example, analog and/or digital video cameras, a video data recorder (VDR) and a pilot display module (MCDU or MIDU). All data is in recorded in an IP format. The IP encoder may be an integral component of the VDR, or the data may be transmitted in an IP format from the data generator device. The VDR includes one or more non-volatile memory arrays for storing and processing the data. The VDR includes both wired and wireless network connectivity. The memory arrays are in a hardened hermetic assembly while other support electronics may be housed in a less rigorous assembly. An underwater beacon generator may be provided to assist in locating a downed VDR unit. The system is adapted for sending live signals directly to ground support via radio or satellite communications channels. The system also includes audio sensors and component monitoring sensor devices and can replace the CVR system where desired. The system is adapted for selectively transmitting all of the data on a near real time basis to a ground tracking station. The system also includes audio sensors and component monitoring sensor devices and can replace the CVR system where desired. The system is adapted to provide access to serial, synchronized full screen view of each of the cameras, in sequence, or alternatively to provide split screen viewing of a plurality of cameras.

CROSS REFERENCE TO RELATED APPLICATION

[0001] This application claims the priority of U.S. ProvisionalApplication Ser. No. 60/428,386, filed on Nov. 22, 2002.

BACKGROUND OF INVENTION

[0002] 1. Field of Invention

[0003] The subject invention is generally related to safety andsurveillance equipment for aircraft and is specifically directed to acomprehensive multi-media flight recording and playback system forcommercial aircraft wherein data and/or video images may be collected,monitored, transmitted, stored and replayed for event reconstruction.

[0004] 2. Discussion of the Prior Art

[0005] Aircraft safety is of ever increasing importance. This isparticularly true with respect to commercial airlines as more and morepeople and freight are moved in this manner. The airways are becomingincreasingly crowded with traffic. Global tracking systems are now inplace to monitor the flight of the aircraft from the moment it lifts offuntil it safely lands at its destination. Radar and global positioningsystems are commonplace both on the aircraft and at the ground trackingstations. All of these electronic systems have increased the overallsafety record of commercial traffic to new standards as the number ofmiles flown continues to escalate at an alarming pace.

[0006] In addition, the on board avionics, including electronicmonitoring and diagnostic equipment, particularly on large commercialjets, continues to evolve giving both the on board crew and the trackingstation more complete, accurate and up-to-date information regarding thecondition of the aircraft while in flight. Flight recorders long havebeen incorporated in order to provide a record of each flight and inorder to provide critical information to aid in the determination of thecauses of an accident or malfunction should one occur.

[0007] One of the greatest safety investigation inventions for thecommercial airline industry has been the crash protected flightrecorder, more commonly called the “Black Box.” Today, flight recordersfor accident investigation are mandatory pieces of equipment in civilaircraft. Flight recorders have changed in design and airline usefulnessduring the past 40 years.

[0008] Efforts to require crash-protected flight recorders date back tothe 1940s. The introduction of Flight Data Recorders (FDR), however,experienced many delays, first being mandated in 1958. The initialrequirement for these data recorders was to record the actual flightconditions of the aircraft, i.e., heading, altitude, airspeed, verticalaccelerations, and time. These early devices had very limited recordingcapabilities. The five analog parameters mentioned above were embossedonto a metal foil, which was used only once. With just five parameters,however, there were not enough recorded data for meaningful accidentinvestigation. Consequently, in 1987, these recorders becameunacceptable to most government regulatory authorities and additionalparameters were required.

[0009] Although most major airlines replaced these old technologyrecorders long before required by law, many of the first generationrecorders are still flying in older model aircraft. The remainder ofthese foil recorders will soon be unusable, since the metal foil isbeing quickly depleted.

[0010] Further, the flight data alone cannot provide all accidentinformation needed by investigators. An advanced technology covering therecording of sounds in the cockpit, crews' conversations, air trafficcontrol communications and aircraft noises is required. This initiateddevelopment of the second next generation of recorders that use magnetictape as the recording medium. The first product to use this newtechnology was the cockpit voice recorder (CVR). In 1965, all commercialoperators were mandated to install a CVR, which would retain the last 30minutes of crew voice communications and noises within the cockpitenvironment. The magnetic tape required very complex fire and crashprotection.

[0011] The Fairchild CVR, Models A100 and A100A, manufactured by L-3Communications Aviation Recorders, are examples of second generationrecorders. These have become the most widely used CVR in the world andhave now been in service for more than 30 years. More recently, thissame “tape” technology has been expanded to the flight data recorder.This second-generation FDR records additional flight parameters whilemeeting higher crash and fire protection requirements than the firstgeneration FDR's, including operational data for engines, flightcontrols, flaps and other operating components to fully assist accidentinvestigators. By the mid 1980s, all newly Type Certified (TC) aircraftwere being fitted with recorders that could capture between 17 to 32parameters.

[0012] In 1990, the third generation Solid State Flight Data Recorder(SSFDR) became commercially practical. The SSFDR, Model F1000, was thefirst certified flight recorder to use this new technology. The SolidState CVR (SSCVR) became available in a 30-minute format in 1992 and ina two-hour format in 1995.

SUMMARY OF THE INVENTION

[0013] The subject invention is directed to a recording and playbacksystem wherein data, video, audio and/or images are multiplexed andsequenced in order to provide a detailed record of the time of an event,the altitude and geographic location of the aircraft and the type andlocation of the event within the aircraft, greatly enhancing eventreconstruction efforts. The terms VDR, Multimedia Flight Data Recorder,IP Data are used interchangeably to refer to this system. The system isa comprehensive multi-media safety and surveillance system, which in thepreferred form provides both visual and audio information as well ascritical data to the flight crew, and to a ground tracking station, andalso permits recording the information and data generated during flightfor archival purposes and for later playback, particularly useful inreconstructing catastrophic events. In one preferred embodiment, aplurality of sensor units, including at least one video imagesensor/device, are placed strategically throughout the aircraft. Forexample, several video cameras may be placed such that the lens of eachis aimed through an opening provided in the fuselage in order to providevideo imaging of the engines, tail section, and landing gear and otherfunctional components of the aircraft. Additional cameras may be placedthroughout the interior of the aircraft on the flight deck, in the cargohold, in the passenger cabin and other desired spaces. The datasensors/transducers, such as by way of example, the engine temperaturesensor, oil pressure and hydraulic pressure sensors, strain gauges andthe like, are also incorporated in the data collection system of thesubject invention. Audio may also be digitized, such as cockpit audio,radio audio, and microphone audio, and stored in the data collectionsystem. This can thus combine the function of the previous generationCockpit Voice Recorder (CVR) into the Multimedia Flight Data Recorder(MFDR) of the subject invention.

[0014] In an additional preferred embodiment, the Multimedia Flight DataRecorder described by this invention also records data from conventionalFlight Data Acquisition & Management System (FDAMS), Digital Flight DataAcquisition Unit (DFDAU), and Aircraft Condition Monitoring System(ACMS). These conventional systems would be interfaced with the I/PFlight Data Recorder of this invention utilizing I/P (InternetProtocol). The conventional systems above, typically interfaced withprotocols ARINC 429, ARINC 573, ARINC 724, ARINC 724B, ARINC 739, ARINC740 and the like, would be converted to I/P protocol for transmission tothe Multimedia Flight Data Recorder of this invention. This provides adramatic improvement in data collection techniques by utilizing highlyflexible LAN techniques for the transmission of and storage of aircraftsafety data. This converted data can be stored in conjunction with otherLAN data such as streaming motion video, step video (still images),streaming audio and event data such as alarms.

[0015] In summary, the Multimedia Flight Data Recorder can recordconventional flight data, video data, image data, audio data and eventdata in any selection or combination as communicated over the aircraftLAN to the Multimedia Flight Data Recorder. The Flight Data Recorder mayalso play back data simultaneously to recording operations, such as forreference to the pilots or to ground analysts during emergencysituations.

[0016] The system may be hardwired in the aircraft, or may use wirelesstransmission and receiving systems. The wireless system is particularlyuseful for adapting the system as a retrofit on existing aircraft andalso provides assurances against disruption of data transmission andcollection during a catastrophic airframe failure. In the preferredembodiment, the wireless system is fully self-contained with each sensorunit having an independent power supply and where appropriate, a sensorlight source. The ground link, monitoring and recording systems forcollecting and transmitting the data are also self-contained. Thisassures that the system will continue to operate in the event of eithera malfunction, such as a total power failure, or a structural failure ofthe aircraft causing a disruption in power source, power wiring orsignaling wiring and will not disrupt the generation and collection ofdata and visual images.

[0017] A monitor may be provided on the flight deck and recorders may beplaced in the tail section, as is common for flight data and voicerecorders currently in use. The flight deck would have instant liveaccess to all of the images as they are captured by the video camerasand/or flight sensors and the recorder would make an historic record ofthe images and data for archive purposes. Where random access recordingtechniques are used, such as, by way of example, digital random accessmemory storage devices, the flight deck and the ground station may alsobe able to search and retrieve stored information. For example, currenthydraulic pressure of a component may be compared with the pressure of apast point in time to monitor rate of change.

[0018] Where desired, ground tracking or control stations would haveselective access to the images on a near or real-time basis. Inaddition, the ground station could send video images to the aircraftflight deck monitors on a selective basis. That is, the ground trackingstation will have the capability of interrogating the in-flight data,including video images, while the aircraft is in flight. Near real-timedata can be received and historical data can be retrieved as well, whenthe random access storage device is utilized.

[0019] The plurality of sensors are synchronized through an on-boardmultiplexing system whereby the plurality of data, including visualimage data, may be displayed, recorded, and/or transmitted with knowntime criteria for each element of data. In the preferred embodiment, thesystem is adapted for incorporating the data signal generated by theaircraft navigational data such as that provided by the on-board globalpositioning system for tracking the altitude, latitude and longitudecoordinates synchronized with the collected data in order to provideaccurate information of where the aircraft is in its flight plan when anincident occurs. A time or chronology signal may also be incorporated inthe data scheme. Any signal that is capable of being captured and storedmay be monitored in this manner. For example, radar images that arecurrently displayed on a cockpit monitor can also be transmitted to theground and can be stored in the record of the “black box” recordingsystem on board the aircraft. Transducer signals monitoring pressuresystem and engine components are also be collected for transmission andstorage. Data generated by image sensors ranging from analog videocameras to digital cameras to infrared sensors and the like cancollected and distributed by the system. The system is particularly wellsuited for use in combination with forward linking infrared (FLIR)cameras for producing visual images in darkness. This would beparticularly useful in determining the flight path of the aircraft, bothon board and for later retrieval when incidents occur in low light levelconditions. Some of these features are shown and described in myco-pending application entitled: “Record and Playback System forAircraft”, Ser. No. 09/257,765, filed on Feb. 25, 1999 and incorporatedby reference herein.

[0020] The system of the subject invention provides a comprehensivemulti-media data capture, display, transmission and storage surveillancesystem for the aircraft while in flight, with data readily accessible toboth the flight crew and a ground tracking station. The system isparticularly suited for providing data transmission over a Local AreaNetwork (LAN) onboard the aircraft and in an IP (Internet Protocol)format and is adapted for merging both analog and digital legacy andstate of the art systems into a comprehensive recording and playbacksystem for aircraft.

[0021] In one embodiment of the invention, the capture, retrieval,monitor and archive system is installed utilizing a wirelesstransmitting/receiving system combined with a sensor in order to assurethat transmission will not be lost in the event of a power shutdown or astructural failure causing possible open circuit conditions that couldoccur in a hard wired system. Such a system may be completelyself-contained with an integrated power supply and an integratedillumination system in the case of a video sensor. The illuminationsystem would provide lighting to permit capture of images in the eventthe aircraft power system fails. The communication between the sensorand the Multimedia Flight Data Recorder, in the preferred embodiment,would utilize the industry standards 802.11 or 802.11b or theirpredecessors. These wireless protocols are highly developed for smallsize, provide error correction protocol and sufficient bandwidth forvideo.

[0022] The system is of invaluable service to the flight crew and theground tracking station, providing visual indication of such informationas the operation of the landing gear, for example, or of an engine smokecondition, or of the presence of smoke or fire in the cargo hold. Inaddition, the system provides instant visual access to conditions in thepassenger cabin or in the cargo hold. The ground or tracking station canrelay video information directly to the crew in the event of certainconditions. For example, if a terrorist or terrorist group were onboard, the ground crew would have access to visual informationindicating the conditions in the passenger cabin and cockpit. This wouldpermit the ground crew to ascertain the number of terrorists on board,the types of weapons carried and visual identification of theindividuals without any communication from the flight crew and withoutany flight crew action. Such information is invaluable in determiningthe best course of action for dealing with such a crisis. Further,critical visual information can be transmitted to the flight crew forassisting the crew in dealing with the situation.

[0023] Of course, it is an important aspect of the invention that all ofthe collected data, including any video images, be recorded on theflight recorder to provide an historic video record of the flight. Thisis invaluable in reconstructing the cause of catastrophic occurrencesduring a flight.

[0024] In the preferred embodiment, the system includes a plurality ofstrategically located video image sensors such as, by way of example,analog and/or digital video cameras, a video data recorder and a pilotdisplay module (MCDU or MIDU). In the preferred embodiment, all data isrecorded in an IP format. The IP encoder may be an integral component ofthe recorder, or the data may be transmitted in an IP format from thedata generator device. The recorder includes one or more non-volatilememory arrays for storing and processing the data. The recorder includesboth wired and wireless network connectivity. In the preferredembodiment, the memory arrays are in a hardened hermetic assembly whileother support electronics may be housed in a less rigorous assembly. Anunderwater beacon generator may be provided to assist in locating adowned recorder unit. The system is adapted for sending live signalsdirectly to ground support via radio or satellite communicationschannels. The system also includes audio sensors and componentmonitoring sensor devices and can replace the Cockpit Voice Recorder(CVR) system where desired. The system is adapted for selectivelytransmitting all of the data on a near real time basis to a groundtracking station.

[0025] Discussion of Typical Data Storage Requirements:

[0026] Storage of typical flight data such as altitude, ground speed,air speed, engine parameters and the like does not consume much datastorage capacity, even when samples are recorded every few seconds.Storage of streaming video is, however, intensive. Compression isutilized to reduce the bandwidth of full motion video from the rawbandwidth of 15 MBytePS to lesser rates from 128 KBytePS to 2 MPBytePSbased on compression types and parameter selection. The most popularcommercial video compression standards are now MPEG, the Motion PictureExperts Group. High-resolution still frame images, such as JPEG orwavelet, can be utilized to store higher quality images at a lowercapture rate than full motion video. Images compressed to 16 KByte to 32KByte have shown adequate quality for flight video collection.Combinations of full motion video at various frame rates and compressionratios and still frame imagery at various compression rates andintervals may be utilized to optimize image quality and storagerequirements.

[0027] Solid-state non-volatile memory technology is quite dense, and iscontinuing to double in density every few years. One solid-state flashmemory that can be utilized for this invention is the SST CompactFlashtechnology, which is currently available in a 256 MByte package that isapproximately 1.5 inches square and 0.13 inches thick. An array of 16 ofthese modules will provide 4 GByte of storage, enough storage to record16 cameras running at 2 FPS of high quality wavelet compression at 16KBytes per image for over 2 hours in addition to storing flight data.The CompactFlash technology utilized in the preferred embodiment is thatwhich is in the Silicon Storage Technology, Inc. model numberSST48CF256.

[0028] The following applications are fully incorporated herein byreference: Ser. No. Filing Date U.S. Pat. No. 09/005,932 Jan. 12, 199809/005,931 Jan. 12, 1998 09/350,197 Jul, 8, 1999 09/006,073 Jan. 12,1998 09/257,765 Feb. 25, 1999 09/257,769 Feb. 25, 1999 08/729,139 Oct.11, 1996 08/745,536 Nov. 12, 1996 6,009,356 08/738,487 Oct. 28, 19965,798,458 09/005,892 Jan. 12, 1998 09/257,802 Feb. 25, 1999 09/257,766Feb. 25, 1999 09/257,767 Feb. 25, 1999 09/257,720 Feb. 25, 1999

[0029] It is, therefore, an object and feature of the subject inventionto provide a network compatible, comprehensive, multi-media datacollection, storage and playback system for aircraft.

[0030] It is an additional object and feature of the subject inventionto provide a video record of critical components and areas of anaircraft during flight for archival and retrieval purposes.

[0031] It is an object and feature of the subject invention to provide avideo or other sensor record of surrounding periphery of the aircraftsuch that a missile attack to that aircraft can be recorded foridentification.

[0032] It is yet another object and feature of the subject invention toprovide apparatus for permitting ground personnel to receive nearreal-time video images, audio information and/or data relating tocritical components and areas of an aircraft during flight.

[0033] It is a further object and feature of the subject invention toprovide apparatus for permitting ground personnel to query, retrieve andreceive historical video images, audio information and/or data relatingto critical components and areas of an aircraft during flight

[0034] It is a further object and feature of the subject invention toprovide accurate information of where the aircraft is during a flightpath when a specific visually captured image occurs.

[0035] It is a further object and feature of the subject invention toprovide accurate information of where the aircraft is during a flightpath when a specific event occurs.

[0036] It is also an object and feature of the subject invention toprovide a system for linking recorded video images with an inertialnavigation system such or other navigational data source such as, by wayof example, a global positioning system for archival purposes.

[0037] It is still another object and feature of the invention to permitthe monitoring, storing and retrieval of any of a variety of videoimages, audio signals and performance data by the tracking, surveillanceand imaging equipment on board the aircraft.

[0038] It is an object and feature of the invention to convert on boardnavigation and safety equipment interface buses such as industrystandard ARINC 429, ARINC 573, ARINC 724, ARINC 724B, ARINC 739, ARINC740 to an I/P connection, such as Ethernet 10/100 BASE-T and the like,for distribution throughout the aircraft and to the flight recorder.

[0039] It is a further object and feature of the invention to convert onboard navigation and safety equipment data streams and files such aretypically communicated on industry standard ARINC 429, ARINC 573, ARINC724, ARINC 724B, ARINC 739, ARINC 740 formats, to data filescommunicated over an I/P connection, such as Ethernet 10/100 BASE-T andthe like, for recording on an industry standard file serverarchitecture, such as Unix or Windows NT architecture, within a hardenedMultimedia Flight Data Recorder.

[0040] It is an object and feature of the invention to power one or moreremote sensors with a standby battery that is in wireless communicationwith the data recorder apparatus which also has standby battery power toenable operation of the data collection system for a period of timeafter the aircraft has had a power failure or wiring failure due tofire, airframe failure, explosion, sabotage or the like.

[0041] It is an object and feature of the invention to utilize 802.11,802.11b or a predecessor standard for data transmission between thesensor and the Multimedia Flight Data Recorder.

[0042] It is an object and feature of the invention to utilize a simplemodification to the 802.11 standard for use exclusively for aircraft andairport security such that commercial 802.11 industry standard productwould not interfere with data transmissions in the aircraft and airportsystems.

[0043] It is an object and feature of the invention to minimize thenumber of electrical signals (wires) that are necessary to interconnectthe to the hardened portion of the aircraft data recorder by utilizationof I/P for the interconnection between the mass memory array and therest of the system electronics for the purposes of simplifying thehermetic sealing and hardening of the mass memory array.

[0044] It is an object and feature of the invention to be a hardenedfile server that can be utilized to store important data that may berequired to be maintained after the recorder is subjected to an intenseevent, such as an airplane or train crash, fire, explosion, or otherenvironmentally severe event.

[0045] Other objects and features of the subject invention will bereadily apparent from the accompanying drawings and detailed descriptionof the preferred embodiments.

BRIEF DESCRIPTION OF THE DRAWINGS

[0046]FIG. 1 is a perspective view of a digital VDR incorporating thebasic features of the subject invention.

[0047]FIG. 2 is a cutaway view of the VDR of FIG. 1.

[0048]FIG. 3 is a block diagram of multiple image collection systemutilizing the teachings of the subject invention.

[0049]FIG. 4 is a modified system with discrete device encoders.

[0050]FIG. 5 is a perspective view of a modified digital multimediaflight data recorder with network connectivity.

[0051]FIG. 6 is a cutaway view of the multimedia flight data recorder ofFIG. 5.

[0052]FIG. 7 is a block diagram of the system of the subject inventionin combination with a legacy flight data acquisition and managementsystem (FDAMS).

[0053]FIG. 8 is an expansion of the block diagram of FIG. 6, showingadditional sensor, communications and display combinations.

[0054]FIG. 9 is a block diagram showing LAN and wireless LAN (WLAN)capability.

[0055]FIG. 10 is a block diagram showing direct LAN connections to thememory array in the multimedia flight data recorder.

[0056]FIG. 11 is a block diagram of the protocol converter that convertsAIRINC standard buses to industry standard LAN networks.

[0057]FIG. 12 is a block diagram depicting the preferred embodimentshown in schematics of FIGS. 16A-16Z and 17A-17M.

[0058]FIG. 13 is the block diagram of the high-density flash memoryarray.

[0059]FIG. 14 is a block diagram of the “black box” circuitry of arecorder in accordance with the subject invention.

[0060]FIG. 15 is a block diagram of the connections incorporated in atypical modular system having the data recorder of the subjectinvention.

[0061]FIGS. 16A to 16Z are the schematic of the support electronicsmodule of the preferred embodiment as shown in FIG. 12.

[0062]FIGS. 17A to 17M are the schematic of the hardened memory moduleof the preferred embodiment as shown in FIG. 12.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0063]FIG. 1 is an illustration of VDR in accordance with the teachingsof the subject invention and includes a hardened hermetic assembly 10for housing the nonvolatile memory units or boards 12, see FIG. 2. Intypical application, the term hardened refers to an assembly that canwithstand the following conditions:

[0064] 60 minutes high temperature fire exposure at 1100° C.;

[0065] 10 hours low temperature fire exposure at 260° C.;

[0066] 30 days of deep water immersion at a depth of 20,000 feet;

[0067] impact shock survival of 3400 Gs;

[0068] impact drop survival of 500 pounds dropped from 10 feet; and

[0069] penetration and static crush of 5000 pounds.

[0070] Standards and specifications may be found in Minimum OperationalSpecifications (MOPS) of TSO C-123a/C124a and Eurocae ED-56/55A.

[0071] In the subject invention, the boards are encased in an insulatingenvelope 14 and are sealed in a thermal mass 16. The outer wall or coverof the assembly 10 is a water-resistant, crush-resistant fire-resistantcase. The support electronics are mounted in a separate support housing18 that may be non-hardened and non-hermetic, if desired. The VDR ismounted on the airframe by suitable mounting means such as the integraltab mounts 20. The power and control coupling 22 and data or video inputcoupling 24 are mounted in the support housing.

[0072] The basic configuration of the invention is shown in FIG. 3. TheVDR 10 includes a power input as previously indicated at 22, a combinedmultiple video/still input system for supporting a plurality of camerasC1, C2, C3, and C4, a control input/output signal line 26 and avideo/still output line 28. Other video sources, such as radar video,can be connected to the video inputs instead of the cameras as show. Thecontrol and output lines are connected to the cockpit user interfacecontroller 30 and a pilot display such as the MCDU or MIDU display 32.The controller 30 can have user interface keys for control of thesystem.

[0073] The memory array is contained in the hardened hermetic assembly10. The controller supplies power and a data interchange bus to thememory array in the hardened housing. In this embodiment, an acousticlocator transmitter device 34 is attached to the exterior of thehardened housing to provide for assistance in locating the VDR during aninvestigation.

[0074] An enhanced configuration of the system is shown in FIG. 4. Inthis configuration, each of the video devices C1, C2, C3 . . . Cn isconnected to a front-end analog signal processor in the VDR for decodingand digitizing the raw data signal and entering it into the videodigital encoder 38 for converting the raw data signal into a compressedvideo digital data stream. The plurality of encoder digital outputsignals are combined at a multiplexer 40 for providing a combinationsignal that is introduced into a processor 42 for managing anddistributing the signal. The signal is sent through a suitableinterface, hermetic connector 44, an additional interface to a memorymanager/processor 45 for distributing the signal to the nonvolatilememory arrays A1, A2, A3 . . . AN. The signal is also entered into avideo digital decoder 46 for output through the video connector 24 tofacilitate display of real time data from the selected video input orarchival data recalled from the hardened memory array. The control inputdata from the pilot or automated systems is introduced to the processor42 through the controls interface 48. System power is provided to thepower supply 50 which powers the entire system and memory array andtypically will include a rechargeable battery system. The acousticlocator 34 also includes an integral backup power supply and battery 54.

[0075] In a preferred embodiment of the multimedia flight data recorder,it is an important feature of the invention that the digital data signalis in a network IP protocol and can be distributed over a wired LANand/or wireless LAN as shown in FIGS. 5, 6, 8 and 9. In thisconfiguration, the multimedia recorder includes a wired LAN port 56 anda wireless LAN access point such as the receiver/transmitter 58.

[0076] A hub 62 configuration is shown in FIG. 7 and illustrates thesystem of the subject invention utilizing digital encoded cameras C1-Cn.The Multimedia Flight Data Recorder can also be used in combination witha legacy flight data acquisition and management system such as (FDAMS)60. The FDAMS system is an aircraft interface for collecting anddistributing data. An example of a FDAMS system is the Honeywell ModelPN 967-0212-002 or the Honeywell Model PN 967-0214-001 that is a fullyintegrated digital flight data acquisition unit and aircraft conditionmonitoring system with PC card extractable data storage. By combiningthis system with the data recorder of the subject invention, the datatypically stored and managed in FDAMS is also transmitted to the datarecorder 10 and through the data recorder management system to the pilotdisplay MCDU or MIDU 32. Various IP sensors such as the camera C1 . . .Cn and other IP devices are connected to a central hub 62 from which acombined input signal 64 is sent over an IP LAN or IP WLAN to the datarecorder 10. Control signals are also sent over the LAN connection 64.

[0077] A fully enhanced system is shown in FIG. 8. This incorporates thelegacy FDAMS system 60, legacy analog cameras AC1 . . . ACn, variousaudio devices interconnected through the audio encoder 70 and the IPcameras C1 . . . Cn in a comprehensive system. The system also includesa wireless panic button system as more fully shown and described in myco-pending application Ser. No. 09/974,337, entitled: “NetworkedPersonal Security Device”, filed on Oct. 10, 2001 and incorporatedherein by reference. Additional output links include SATCOM capability82 for transmission to ground control, a military radio link 80 and awireless LAN access point 78 for communication with the terminal andchase aircraft or other pursuit transports. Specifically, the variousradio transceivers may include multiple radio channel, a speaker systemand various microphone or acoustic devices, all of which feed into anaudio encoder 70 to convert the discrete signals into a combined IPsignal at 72. The various analog cameras AC1 . . . ACN produce rawsignals introduced into a video encoder 74 for producing an IP signal at76. The IP signals are introduced to a switch hub 62. The signals fromthe IP cameras C1 . . . Cn are introduced to the switch hub. IP devicesmay also be connected to the system via wireless LAN as well as wiredLAN. The wireless devices such as wireless IP cameras WC1 and WC2produce a wireless signal received by an access point 76 for introducingthese signals to the hub 62. The hub then distributes a combined IPoutput signal to the wireless LAN access point 78, the military radiointerface 80 and the SATCOM interface 82, as well as the data recorder10. The panic buttons B1 . . . Bn via the wireless access point orpoints 84. This signal is also sent to the various receiving stationsand as disclosed in by co-pending application can be both an alertsignal and a control signal.

[0078]FIG. 9 shows an enhancement including a LAN controllerconfiguration. In this configuration the output signals are introducedinto a memory selector 86. The memory selector distributes output to aLAN interface 88 managed by processor 90. The LAN interface is connectedto a switch hub 92 for distributing the signals to the aircraft LAN 94,the aircraft fiber LAN 96 through the fiber interface 98 and an ARINC573 or the like via the ARINC interface 100. The hub 92 also distributesthe signal via a wireless LAN access point 102 to the wireless LAN viathe antennas 104.

[0079]FIG. 10 shows an enhancement with direct LAN to memory capability.This is a preferred configuration because it minimizes the number ofwires that is required to enter the hardened memory array. In thisconfiguration, the communication with the switched hub 92 is over a LANsignal line 105 and through a LAN interface 106 directly to the memorymanager processor 45, fully implementing the IP protocol capability ofthe system.

[0080]FIG. 11 shows a plurality of aircraft interface bus standardsbeing bridged to an industry standard LAN protocol in order tocommunicate with the preferred embodiment of the Multimedia Flight DataRecorder or other LAN devices. Note that the protocol can be adapted toprovide bridging of one or more protocols, such as Ethernet, AIRINC 429,ARINC 573, AIRINC 724/724B, ARINC 739, MIL-STD 1553B, and the like. Theprotocol conversion would communicate to the devices on the buses in thenative protocol, strip the data and store it in the processor RAM, thentransmits it out utilizing another protocol over another bus.

[0081]FIG. 12 is a preferred embodiment of the invention and is a blockdiagram as supported by the schematics of FIGS. 16 and 17. The circuitryis separated into main assemblies, the Support Electronics (see FIG. 16)and the Hardened Memory Array (see FIG. 17). The interface between thetwo is Ethernet in this preferred configuration. The Support Electronicsand Hardened Memory Array can be directly tied, or can be passed throughan optional switch or hub that allows interconnection to other LANdevices. There are several advantages in utilizing a standard LANconnection such as Ethernet as the interface into the Hardened MemoryArray. One advantage is that there are a minimum number of wired thatare required through the problematic hermetic connector into theHardened Memory Array. Another advantage is that the Hardened MemoryArray can be easily interfaced for production, setup, diagnostic andreadout functions by plugging other LAN devices directly into theHardened Memory Data Array. Of course data can be protected fromunauthorized reading or tampering with system passwords and encryption.

[0082]FIG. 13 shows a high density flash card configuration such as the“CompactFlash Card data sheet from SST. The highest density card fromthis company is 256 megabytes on one module.

[0083]FIG. 14 shows the black box circuitry of the system. The GPSreceiver 33, Panic Button transmitter/receivers 88, video multiplexer136, and IP video multiplexer 132 are all in communication with thecontroller/processor 130. The IP video multiplexer 132 is also incommunication with the multiplexer 138 (see connector cable 134) fordistributing the signal via an IP interface 140 to a LAN interface 142.An Audio signal may also be distributed, see audio decoder 143.Connectivity to a control panel 72 is also shown. A typical modularcommercial system is shown in FIG. 15.

[0084]FIGS. 16A to 16Z are the schematic of the support electronicsmodule of the preferred embodiment as shown in FIG. 12.

[0085]FIGS. 17A to 17M are the schematic of the hardened memory moduleof the preferred embodiment as shown in FIG. 12.

[0086] While certain features and embodiments of the invention have beendescribed in detail herein, it will be readily understood that theinvention includes all modifications and enhancements within the scopeand spirit of the following claims.

What is claimed is:
 1. An aircraft video data recorder system,comprising: a. A digital memory array; b. A signal generating devicelocated strategically in the aircraft; c. A coupler for receiving datasignals from the signal generating device; d. An encoder for convertingthe data signals to an IP protocol; and e. An interface for introducingthe IP protocol signals to the memory array.
 2. The system of claim 1,wherein the encoder is located at the VDR.
 3. The system of claim 1,wherein the encoder is located at the signal generating device.
 4. Thesystem of claim 1, wherein the signal generating device is an IPprotocol camera.
 5. The system of claim 1, wherein the signal generatingdevice is an analog camera further including a digital signal encoder.6. The system of claim 1, wherein the signal generating device is ananalog audio transmitter further including a digital signal encoder. 7.The system of claim 1, wherein there are further included a plurality ofsignal generating devices, each of said devices generating a discretesignal and wherein there is further including a multiplexer forcombining the signals into a single signal for transmission to thememory.
 8. The system of claim 1, wherein there are further included aplurality of dissimilar signal generating devices and there is furtherincluded a switched hub for managing the signals therefrom.
 9. Thesystem of claim 1, wherein the signal generating device is a wirelessdevice and wherein there is further included a wireless access pointassociated with the system for transmitting the wireless signal from thewireless device to the system.
 10. The system of claim 1, wherein thesignal generating device is a legacy flight data acquisition andmanagement system.
 11. The system of claim 1, further including a panicbutton device for sending an alert signal to the system when activated.12. The system of claim 12, wherein the alert signal is also a controlsignal for controlling distibution of the output signals from the VDRwhen the panic button device is activated.
 13. The system of claim 1,further including a communication link for sending the data signals toan external receiving station.
 14. The system of claim 13, wherein thecommunication link is a communications satellite interface.
 15. Thesystem of claim 13, wherein the communication link is a military radio.16. The system of claim 13, wherein the communication link is a wirelessLAN.
 17. The system of claim 1, further including an output linkdirectly to a LAN interface for distributing the data signals.
 18. Thesystem of claim 17, further including a switch hub for distributing theoutput signals via the LAN interface.
 19. The system of claim 18,including an ARINC link for receiving the distributed output signalsfrom the LAN interface.
 20. The system of claim 18, including anaircraft LAN for receiving the distributed output signals from the LANinterface.